CN102494564A - Method for designing miniature forward tracking and intercepting tail seeker head - Google Patents
Method for designing miniature forward tracking and intercepting tail seeker head Download PDFInfo
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- CN102494564A CN102494564A CN2011104065637A CN201110406563A CN102494564A CN 102494564 A CN102494564 A CN 102494564A CN 2011104065637 A CN2011104065637 A CN 2011104065637A CN 201110406563 A CN201110406563 A CN 201110406563A CN 102494564 A CN102494564 A CN 102494564A
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- tail
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- target seeker
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- seeker
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Abstract
The invention discloses a method for designing a miniature forward tracking and intercepting tail seeker head. An interceptor consists of a seeker head, an interceptor head, a primary thruster, a secondary thruster and a tail wing, wherein the seeker head is fixed on the tail part of the interceptor head, and a detecting window is formed backward; a position marker in the seeker head consists of a fairing, a front lens set, a reflector group, a rear lens set and a wave band sorter which are arranged sequentially; the fairing is covered outside the front lens set; and the front lens set, the reflector group and the rear lens set are fixed in the seeker head respectively, so that a pitching optical axis is coincided with a pitching mechanical axis, and a roll mechanical axis is coincided with a roll optical axis. Due to the adoption of a scheme and a miniature design of the tail seeker head, the optical axis is coincided with an interceptor axis, light rays are reflected, introduced and fixed on a focal plane of a detector of an interceptor body through a plurality of complex light paths during platform pitching change, the detecting precision is ensured, and mounting convenience of the tail seeker head is improved.
Description
Technical field
The present invention relates to
OnePlant new forward direction tracking interception tail and put target seeker miniaturization Design method, can be used for anti-hypersonic vehicle interceptor, belong to areas of information technology.
Background technology
Along with the development of military technology and the application of new and high technology, the use of tactical ballistic missile (TBM) has been used as a kind of effective attack means.Developing the air defence missile with effective anti-ballistic ability has become the focus of one of most important defense strategy of world today military power and armament competition.
For effective killer T BM, must realize the direct collision of air defence missile and TBM.For the lower aircraft of speed, generally adopt rear side to following the trail of interception mode, target seeker is preposition, and the target seeker detection window is arranged on the front end of bullet, bumps from proceeds posterolateral and target aircraft.But,,, adopt rear side too high to the rate request of interceptor, and receive pneumatic heat affecting bigger to the tracking interception mode because target velocity is very high for superelevation velocity of sound weapon.At present, be more prone to adopt forward direction to follow the trail of the interception mode (see figure 1),, reduce aerothermal influence simultaneously to reduce the speed of interceptor.
The THAAD of the U.S. (THAAD) is a kind of typical high-altitude long-range anti-TBM system, and it adopts infrared homing terminal guidance.And this type of air defence missile is with the flight of very high speed, and pneumatic heat is serious, if the target seeker detection window is directly installed on head, aero-optical effect will cause the infrared seeker can't operate as normal.In order to reduce the influence of pneumatic heating, adopt blocker side window Detection Techniques at present, this method mainly is to be arranged in the target seeker detector window side (see figure 2) of bullet, thereby makes detection window avoid front end thermal boundary.The side that detector window is arranged in bullet can cause sight line asymmetric, needs to coordinate the control of missile attitude and track, improves the guidance precision of air defence missile flight latter end, and the design of control system is had higher requirement.Therefore air defence missile of new generation mainly adopts active target seeker or optical seeker technology and advanced missile guidance control technology.
In said method, rear side is too high to the rate request of interceptor to the tracking interception mode, and pneumatic heat is serious.At this moment, if the detection window of target seeker is arranged in the front end of bullet, aero-optical effect will cause the infrared seeker can't operate as normal.Adopt forward direction to follow the trail of interception mode, can reduce the speed of interceptor, also reduced aerothermal influence simultaneously.If the detection window of target seeker is arranged in the front end of bullet, can't survey target.At present, follow the trail of under the interception mode, the target seeker detection window is arranged in the side of bullet, thereby makes detection window avoid front end thermal boundary at forward direction.But the side that detector window is arranged in bullet can cause sight line asymmetric, need to coordinate the control of missile attitude and track, and the fly guidance precision of latter end of interceptor has been proposed very high requirement.
Summary of the invention
Based on above elaboration; The purpose of this invention is to provide a kind of employing guiding and put scheme end to end, the target seeker detector arrangement is terminal at bullet, be in before the firsts and seconds propelling; And carry out miniaturization Design, when guaranteeing detection accuracy, improve tail and put the convenience that target seeker is installed.
For realizing above-mentioned purpose; The technical scheme that the present invention takes is, a kind of forward direction is followed the trail of the interception tail and put target seeker miniaturization Design method, interceptor by target seeker, bullet, one-level advance, secondary advances and empennage is formed; Target seeker is fixed in the afterbody of bullet, and detection window backward; Position marker in the target seeker is made up of the radome fairing that sets gradually, preceding mirror group, reflector group, back mirror group and wave band sorter; Radome fairing covers in outside the preceding mirror group; Before mirror group, reflector group, back mirror group fixing in target seeker respectively, and make that the pitching optical axis of its formation overlaps with the pitching mechanical axis, roll mechanical axis and roll optical axis coincidence.
At first, adopt forward direction to follow the trail of interception mode, tail is put target seeker.
The employing two-stage advances, and the target seeker detection window is arranged in the end of interceptor bullet, one-level advance with the secondary propelling before.After the two-stage propelling came off, interceptor was positioned at target the place ahead, and target seeker passes through detection window captured target backward.
Secondly, for facility is installed, and guarantee precision, target seeker is carried out miniaturization Design.
In order to realize the miniaturization of target seeker, position marker adopts small-sized pitching lift-over diaxon position marker form, stares detector and inertial measurement cluster is fixed in body.Imaging under this kind structure during for implementation platform pitching variation and position marker lift-over needs to guarantee that optical axis overlaps with the bullet axle, and the light when the platform pitching changed is fixed on the detector focal plane of body through the introducing of turning back of the repeatedly light path of complicacy.
To the general technical requirement, learn material, mechanical lens barrel material poor, the achromatism of heat that disappears through excellent luminous intensity distribution; Make the optical system radial dimension reduce to minimum through the secondary imaging technology; Through using symmetrical mirror group balance spherical aberration, coma, optical system imaging quality is issued to diffraction limit in the general requirement condition.
The range of application that the present invention is possible: the anti-hypersonic vehicle interceptor forward direction of doing wartime in the endoatmosphere is followed the trail of in the interception.
The invention solves forward direction, to follow the trail of under the interception mode target seeker side window Detection Techniques sight line asymmetric; Guidance precision to interceptor flight latter end requires very high problem; Guaranteeing that adopting the miniaturization Design method to improve tail under the situation of precision puts target seeker installation convenience, has avoided the target-seeking Detection Techniques of infrared imaging in the endoatmosphere because the high-speed flight meeting produces pneumatic thermal phenomenon around the blocker head-shield.
Description of drawings
Fig. 1 is that forward direction is followed the trail of the interception mode sketch map;
Fig. 2 is existing side window target seeker sketch map;
Fig. 3 is the position view of target seeker 1 among the present invention;
Fig. 4 is the optical system position marker sketch map of target seeker 1 among the present invention;
Among the figure: 1, target seeker, 11, radome fairing, 12, preceding mirror group, 13, reflector group, 14, back mirror group, 15, the wave band sorter, 2, bullet, 3, one-level advances, 4, secondary advances, 5, empennage.
Specific embodiment
Below in conjunction with accompanying drawing and embodiment the present invention is described further; Referring to Fig. 3 and Fig. 4; A kind of forward direction is followed the trail of the interception tail and is put target seeker miniaturization Design method; Interceptor is made up of target seeker 1, bullet 2, one-level propelling 3, secondary propelling 4 and empennage 5, and target seeker 1 is fixed in the afterbody of bullet 2, and detection window backward; Position marker in the target seeker 1 is made up of the radome fairing that sets gradually 11, preceding mirror group 12, reflector group 13, back mirror group 14 and wave band sorter 15; Radome fairing 11 covers in outside the preceding mirror group 12; Before mirror group 12, reflector group 13, back mirror group 14 target seeker 1 in, fix, and make that the pitching optical axis of its formation overlaps with the pitching mechanical axis respectively, roll mechanical axis and roll optical axis coincidence.
Embodiment:At first, tail is put the target seeker design.
Referring to Fig. 3, adopt two-stage to advance, with the fixed-site of target seeker afterbody at guided missile warhead, one-level advance with the secondary propelling before, detection window is backward.After the two-stage propelling came off, guided missile was positioned at target the place ahead, and target seeker passes through detection window captured target backward at this moment.
Secondly, target seeker carries out miniaturization Design.
Referring to Fig. 4; This optical system position marker mainly is made up of three parts: preceding mirror group, reflector group, back mirror group; And optical element and machine components are closely glued together, and wherein pitching optical axis and pitching mechanical axis must overlap, and roll mechanical axis and roll optical axis must overlap.In order to realize the miniaturization of target seeker, position marker adopts small-sized pitching lift-over diaxon position marker form, stares detector and inertial measurement cluster is fixed in body.
To the general technical requirement, learn material, mechanical lens barrel material poor, the achromatism of heat that disappears through excellent luminous intensity distribution; Make the optical system radial dimension reduce to minimum through the secondary imaging technology; Through using symmetrical mirror group balance spherical aberration, coma, optical system imaging quality is issued to diffraction limit in the general requirement condition.Optical system is rotated around the pitching mechanical axis through preceding mirror group, reflector group, and whole optical system is the hemisphere spacescan before the roll mechanical axis rotates realization.Pitching optical axis and pitching mechanical axis overlap and are pitch axis, and roll mechanical axis and roll optical axis coincidence are wobble shaft.
Key problem in technology point of the present invention is:
The forward direction that is proposed is followed the trail of the interception guiding and is put scheme end to end.
The forward direction that is proposed is followed the trail of the interception tail and is put target seeker miniaturization Design method.
KKV is a kind of antiaircraft weapon that grows up in order to tackle tactical missile, most target-seeking Detection Techniques of infrared imaging that adopt.Do wartime in the endoatmosphere,, thereby can bring serious detection to disturb the infrared imaging guidance system because the high-speed flight meeting produces pneumatic heating phenomena around the blocker head-shield.This patent proposes a kind of new forward direction tracking interception tail and puts target seeker miniaturization Design method.Original technology mainly adopts blocker side window Detection Techniques, and this method is arranged in the side of guided missile to detector window, thereby makes detection window avoid front end thermal boundary.But this technology because detection window in the side of guided missile, causes sight line asymmetric, needs to coordinate the control of missile attitude and track, and the design of control system is had higher requirement, and can't be used for adopting forward direction to follow the trail of the KKV of interception mode.This patent is on original technical foundation; Adopt guiding to put scheme end to end, the target seeker detector arrangement is terminal at bullet, be in before the firsts and seconds propelling; And carry out miniaturization Design; Adopt small-sized pitching lift-over diaxon position marker form, stare detector and inertial measurement cluster is fixed in body, guarantee that optical axis overlaps with the bullet axle; And the light when the platform pitching changed turns back to introduce through the repeatedly light path of complicacy and is fixed on the detector focal plane of body, when guaranteeing detection accuracy, improves tail and puts the convenience that target seeker is installed.
Claims (1)
1. a forward direction is followed the trail of the interception tail and is put target seeker miniaturization Design method; Interceptor advances (3), secondary to advance (4) and empennage (5) to form by target seeker (1), bullet (2), one-level; It is characterized in that target seeker (1) is fixed in the afterbody of bullet (2), and detection window backward; Position marker in the target seeker (1) is made up of the radome fairing that sets gradually (11), preceding mirror group (12), reflector group (13), back mirror group (14) and wave band sorter (15); Radome fairing (11) covers in outside the preceding mirror group (12); Before mirror group (12), reflector group (13), back mirror group (14) target seeker (1) in, fix respectively, and make that the pitching optical axis of its formation overlaps with the pitching mechanical axis, roll mechanical axis and roll optical axis coincidence.
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| CN2011104065637A CN102494564A (en) | 2011-12-09 | 2011-12-09 | Method for designing miniature forward tracking and intercepting tail seeker head |
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| CN2011104065637A CN102494564A (en) | 2011-12-09 | 2011-12-09 | Method for designing miniature forward tracking and intercepting tail seeker head |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105711850A (en) * | 2016-01-30 | 2016-06-29 | 上海仪耐新材料科技有限公司 | Net-bullet type intelligent interception system for resisting unmanned aerial vehicle |
| CN105759439A (en) * | 2016-04-08 | 2016-07-13 | 北京航天计量测试技术研究所 | Infrared refractive-diffractive optical structure suitable for side window imaging |
| CN105783593A (en) * | 2016-05-04 | 2016-07-20 | 北京川瀚科技股份有限公司 | Laser guidance seeker and guiding method based on same |
| CN106705770A (en) * | 2017-02-23 | 2017-05-24 | 西北工业大学 | Guided missile track and posture coordinated control system and method under side window detection conditions |
| CN106934118A (en) * | 2017-02-23 | 2017-07-07 | 西北工业大学 | Guided missile initial transmissions orientation preferentially evaluation system and method under the conditions of Side Window Detection |
| CN109254392A (en) * | 2018-08-22 | 2019-01-22 | 哈尔滨新光光电科技有限公司 | A kind of miniaturization rolling-backstroke long wave refrigeration optical system |
| CN114279268A (en) * | 2021-11-17 | 2022-04-05 | 航天科工微电子系统研究院有限公司 | Kinetic energy interceptor based on head deflection |
| CN114502907A (en) * | 2019-07-31 | 2022-05-13 | Bae系统信息和电子系统集成有限公司 | Wing-mounted seeker |
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| US6561074B1 (en) * | 1977-07-28 | 2003-05-13 | Raytheon Company | Shipboard point defense system and elements therefor |
| GB2469736A (en) * | 2009-04-20 | 2010-10-27 | Sagem Dofense Socurito | Catadioptric homing seeker head with two detection channels for a missile |
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| US6561074B1 (en) * | 1977-07-28 | 2003-05-13 | Raytheon Company | Shipboard point defense system and elements therefor |
| US6209820B1 (en) * | 1998-07-22 | 2001-04-03 | Ministry Of Defense Armament Development Authority | System for destroying ballistic missiles |
| DE10135222A1 (en) * | 2001-07-24 | 2003-02-06 | Bodenseewerk Geraetetech | Arrangement for detecting object scene has detector, imaging system with object side part pivotable about pitch axis by pitch frame pivotable in roll frame mounted about roll axis |
| GB2469736A (en) * | 2009-04-20 | 2010-10-27 | Sagem Dofense Socurito | Catadioptric homing seeker head with two detection channels for a missile |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105711850A (en) * | 2016-01-30 | 2016-06-29 | 上海仪耐新材料科技有限公司 | Net-bullet type intelligent interception system for resisting unmanned aerial vehicle |
| CN105759439A (en) * | 2016-04-08 | 2016-07-13 | 北京航天计量测试技术研究所 | Infrared refractive-diffractive optical structure suitable for side window imaging |
| CN105783593A (en) * | 2016-05-04 | 2016-07-20 | 北京川瀚科技股份有限公司 | Laser guidance seeker and guiding method based on same |
| CN105783593B (en) * | 2016-05-04 | 2017-06-13 | 北京川瀚科技股份有限公司 | A kind of laser seeker and its guidance method |
| CN106705770A (en) * | 2017-02-23 | 2017-05-24 | 西北工业大学 | Guided missile track and posture coordinated control system and method under side window detection conditions |
| CN106934118A (en) * | 2017-02-23 | 2017-07-07 | 西北工业大学 | Guided missile initial transmissions orientation preferentially evaluation system and method under the conditions of Side Window Detection |
| CN106934118B (en) * | 2017-02-23 | 2020-05-19 | 西北工业大学 | Missile initial launching azimuth preferred evaluation system and method under side window detection condition |
| CN109254392A (en) * | 2018-08-22 | 2019-01-22 | 哈尔滨新光光电科技有限公司 | A kind of miniaturization rolling-backstroke long wave refrigeration optical system |
| CN109254392B (en) * | 2018-08-22 | 2019-06-14 | 哈尔滨新光光电科技有限公司 | A kind of miniaturization rolling-backstroke long wave refrigeration optical system |
| CN114502907A (en) * | 2019-07-31 | 2022-05-13 | Bae系统信息和电子系统集成有限公司 | Wing-mounted seeker |
| CN114502907B (en) * | 2019-07-31 | 2023-06-16 | Bae系统信息和电子系统集成有限公司 | Wing mounted seeker |
| CN114279268A (en) * | 2021-11-17 | 2022-04-05 | 航天科工微电子系统研究院有限公司 | Kinetic energy interceptor based on head deflection |
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Application publication date: 20120613 |